EP0727615A1 - Einspritzdüse für die Brennkammer einer Gasturbine - Google Patents

Einspritzdüse für die Brennkammer einer Gasturbine Download PDF

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Publication number
EP0727615A1
EP0727615A1 EP96400310A EP96400310A EP0727615A1 EP 0727615 A1 EP0727615 A1 EP 0727615A1 EP 96400310 A EP96400310 A EP 96400310A EP 96400310 A EP96400310 A EP 96400310A EP 0727615 A1 EP0727615 A1 EP 0727615A1
Authority
EP
European Patent Office
Prior art keywords
chamber
vaporization
dilution
assembly according
oxidant
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP96400310A
Other languages
English (en)
French (fr)
Inventor
Denis Roger Henri Ansart
Denis Jean Maurice Sandelis
Patrice André Commaret
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0727615A1 publication Critical patent/EP0727615A1/de
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

  • FR-A-1 590 542 describes a fuel injection assembly intended to equip a gas turbine combustion chamber, comprising a fuel injector opening into a pre-vaporization chamber and at least two pre-vaporization conduits connected to said combustion chamber pre-vaporization which they connect to two intake orifices of the pre-evaporated mixture in premix chambers which are separate from each other and which are each separate from the pre-vaporization chamber and which open into the combustion chamber, the pre-vaporization chamber being provided with '' inlet ports for oxidizer under pre-vaporization pressure and each premix chamber being provided with an inlet device for oxidizer under dilution pressure.
  • the invention proposes the adoption of a set of provisions making it possible to obtain a pre-vaporization of the injected fuel free from the risk of self-ignition and to produce oxidizer / fuel premixes having riches lower than that of a stoichiometric mixture, further propelled at high speed, preferably with turbulence to ensure, in the combustion chamber, lean and complete combustion.
  • the cross section of the inlet orifice (s) of the pre-vaporization oxidant and the pressure of said pre-vaporization oxidant have values such that the pre-evaporated mixture has a higher richness than that of a stoichiometric mixture, however that the intake section of the dilution oxidizer intake device and the pressure of said dilution oxidant have values such that the mixture contained in each premix chamber has a lower richness than that of a stoichiometric mixture.
  • the main advantage of the invention lies precisely in obtaining a satisfactory, low-pollution combustion, with a reduced production of nitrogen oxides and fumes, and the elimination of the risks of self-ignition and return of flames ("flash-back").
  • This enclosure 6 therefore has an annular configuration with an axis 1.
  • Regularly angularly distributed and fixed to the bottom 4, opening into the combustion enclosure 6, are arranged on the one hand, along an external circular ring, injectors of fuel 7, used for "IDLE” operation, on the other hand, along an internal circular ring, injection assemblies 8, such as those described below, used during "FULL GAS” operation , corresponding, for example, to the takeoff of an airplane.
  • the injectors 7 are separated from the injection assemblies 8 by a median separator 9, and are connected to fuel tanks by conduits 10 and 11, respectively.
  • a source of pressurized oxidizer symbolized by the arrow G, makes it possible to supply the combustion chamber with pressurized oxidizer, to of course burn the fuel, but also used for the cooling of the various walls of the chamber. exposed to high temperatures from combustion.
  • the pressurized oxidant source generally consists of a helical compressor placed upstream of the combustion chamber, driven by the gas turbine, which uses the combustion gases.
  • Figures 2 and 3 show a first embodiment of an injection assembly 4 according to the invention.
  • Two premix chambers 12 are delimited, each by a frustoconical wall 13, of axis A13 substantially parallel to axis 1, fixed on the bottom 4, each wall 13 converging downstream, in the direction of arrow F , having its downstream opening end 14, which opens into the combustion chamber 6.
  • a hollow body 15, of substantially hemispherical shape, is connected to an upstream end opening 17 of each wall 13, an annular space 18 inlet (arrows H1) of oxidizer under pressure being formed between said body 15 and said wall 17.
  • the body 15 is coaxial with the axis A13.
  • Two pre-vaporization conduits 19 are connected, on the one hand, each to one of the bodies 15 by emerging therein coaxially through an orifice 20 for admission of a pre-evaporated oxidant / fuel mixture, on the other hand both in the case present in parallel, to a pre-vaporization chamber 21 constituted by a cylindrical wall 22 of axis A22 parallel to the axis 1.
  • a helical "spin" 24 for admission into the premix chamber 12 of the so-called dilution oxidizer (arrows H2).
  • Each spin 24 has the function of rotating the oxidant passing through it, capable of promoting satisfactory homogeneity of the mixture in the premix chamber 12. Furthermore, a diaphragm 25 is placed near the end 26 through which the pre-vaporization 21 is connected to the two pre-vaporization pipes 19.
  • a fuel supply duct 11 is connected to a fuel injector 27, which opens inside the pre-vaporization chamber 21, towards the diaphragm 25.
  • a protective cap 28 has a main opening 29, which surrounds, in providing an annular space 30, the downstream end 31 of the wall 22 of the pre-vaporization chamber 21, and is thus interposed between the enclosure 6 of the combustion chamber and the whole of the pre-vaporization chamber 21, of the fuel injector 27 which opens into it, and the fuel supply duct 11.
  • Figures 5 and 6 on the one hand, Figures 7 and 8 on the other hand, represent two combustion chambers of gas turbines, in which are used injection assemblies, as described above.
  • the general arrangements of Figures 5 and 7 are known in themselves. It can however be noted that in both embodiments, the small size of the assemblies according to the invention, linked to the fact that a single fuel injector feeds two intake orifices of the mixture evaporated in the chambers of premix, allows optimum distribution of said intake orifices, capable of obtaining satisfactory homogeneity of the oxidant / fuel mixture admitted into the combustion chamber, and consequently capable of obtaining regular and complete combustion.
  • the protective cap 28 constitutes a screen, which protects the fuel injector 27 and the pre-vaporization chamber 21 from the high temperatures prevailing in enclosure 6 of the combustion chamber. This provision is likely to reduce or eliminate hot spots in the fuel injection area, thereby reducing or eliminating the risk of self ignition.
  • the flow of oxidant admitted into the pre-vaporization chamber 21 (arrow H6) (and its pressure) and the flow of fuel injected by the fuel injector 27 are in a ratio such that the mixture evaporated in the pre-vaporization chamber 21 and contained in the pre-vaporization conduits 19 has a richness greater than the richness of a stoichiometric mixture.
  • This pre-evaporated mixture admitted into the premix chambers 12, is stirred with the flow of dilution oxidant passing through the tendrils 24 and the orifices 32, 34 and 36 (arrows H2, H3, H4, H5) and the annular spaces 18 (arrows H1), as also with the oxidizer of the refrigeration multiperforations 38, the resulting mixture, contained in the premix chambers 12 having a richness lower than that of a stoichiometric mixture.
  • the initial pre-vaporization entirely separate from the final mixture, allows obtaining rich, pre-vaporized mixtures, sheltered from the risks of self-ignition and flashback, then a rapid, energetic injection.
  • the downstream orientation of the orifices 20 for admission into the premix chambers 12 of the pre-evaporated mixture naturally facilitates the flow of the mixture downstream.
  • the shape converging downstream of the walls 13 of the premix chambers 12 has the effect of accelerating the propulsion of the mixture towards the combustion chamber so as to promote complete combustion of said mixture.
  • the admission of the oxidizer via the second tendrils 124 replaces the admission through the orifices 32, 34 and 36 of the embodiment of FIGS. 2 and 3.
  • the action of the tendrils 24 and 124 is to promote mixing of the mixture and to ensure good homogeneity thereof, guaranteeing the regularity of the subsequent combustion in the combustion chamber 6.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
EP96400310A 1995-02-15 1996-02-15 Einspritzdüse für die Brennkammer einer Gasturbine Ceased EP0727615A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9501706A FR2730555B1 (fr) 1995-02-15 1995-02-15 Ensemble d'injection de carburant pour chambre de combustion de turbines a gaz
FR9501706 1995-02-15

Publications (1)

Publication Number Publication Date
EP0727615A1 true EP0727615A1 (de) 1996-08-21

Family

ID=9476145

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96400310A Ceased EP0727615A1 (de) 1995-02-15 1996-02-15 Einspritzdüse für die Brennkammer einer Gasturbine

Country Status (3)

Country Link
US (1) US5651252A (de)
EP (1) EP0727615A1 (de)
FR (1) FR2730555B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0893650A2 (de) * 1997-07-23 1999-01-27 General Electric Company Vergaser mit multiplen Verwirbelungsvorrichtungen

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2770283B1 (fr) * 1997-10-29 1999-11-19 Snecma Chambre de combustion pour turbomachine
AU7985600A (en) * 1999-10-12 2001-04-23 Alm Development, Inc. Combustor and method of burning fuel
US6813889B2 (en) * 2001-08-29 2004-11-09 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US6928823B2 (en) * 2001-08-29 2005-08-16 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US6702571B2 (en) 2001-09-05 2004-03-09 Gas Technology Institute Flex-flame burner and self-optimizing combustion system
GB2443429A (en) * 2005-09-24 2008-05-07 Siemens Ind Turbomachinery Ltd Fuel Vaporisation Within a Burner Associated With a Combustion Chamber
US8387390B2 (en) * 2006-01-03 2013-03-05 General Electric Company Gas turbine combustor having counterflow injection mechanism
FR2920032B1 (fr) * 2007-08-13 2014-08-22 Snecma Diffuseur d'une turbomachine
RU2526410C2 (ru) 2009-09-13 2014-08-20 Лин Флейм, Инк. Способ поэтапного изменения подачи топлива в устройстве с камерой сгорания
EP2923150B1 (de) * 2012-11-21 2018-09-05 General Electric Company Flüssigbrennstoffkartusche mit anti-verkokungs-funktion
GB2549170B (en) * 2016-02-05 2021-01-06 Bayern Chemie Ges Fuer Flugchemische Antriebe Mbh Device and System for Controlling Missiles and Kill Vehicles Operated with Gel-like Fuels
FR3101696B1 (fr) * 2019-10-08 2021-10-29 Safran Helicopter Engines Canne de prevaporisation pour une chambre de combustion de turbomachine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2628475A (en) * 1946-06-26 1953-02-17 Socony Vacuum Oil Co Inc Jet combustion device embodying pretreatment of fuel before combustion
US2949012A (en) * 1957-03-01 1960-08-16 Snecma Vaporisation burner device
FR1590542A (de) * 1968-11-04 1970-04-13
US4351156A (en) * 1978-08-02 1982-09-28 International Harvester Company Combustion systems
US5133192A (en) * 1989-08-31 1992-07-28 Rolls-Royce Plc Fuel vaporizer
FR2691235A1 (fr) * 1992-05-13 1993-11-19 Snecma Chambre de combustion comprenant un ensemble séparateur des gaz.
FR2695713A1 (fr) * 1992-09-17 1994-03-18 Snecma Système d'injection aérodynamique à prémélange.

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3570242A (en) * 1970-04-20 1971-03-16 United Aircraft Corp Fuel premixing for smokeless jet engine main burner
NL7801395A (nl) * 1977-02-23 1978-08-25 Foerenade Fabriksverken Werkwijze en inrichting voor het verbranden van vloeibare, gasvormige of poedervormige brandstoffen.
US5444982A (en) * 1994-01-12 1995-08-29 General Electric Company Cyclonic prechamber with a centerbody

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2628475A (en) * 1946-06-26 1953-02-17 Socony Vacuum Oil Co Inc Jet combustion device embodying pretreatment of fuel before combustion
US2949012A (en) * 1957-03-01 1960-08-16 Snecma Vaporisation burner device
FR1590542A (de) * 1968-11-04 1970-04-13
US4351156A (en) * 1978-08-02 1982-09-28 International Harvester Company Combustion systems
US5133192A (en) * 1989-08-31 1992-07-28 Rolls-Royce Plc Fuel vaporizer
FR2691235A1 (fr) * 1992-05-13 1993-11-19 Snecma Chambre de combustion comprenant un ensemble séparateur des gaz.
FR2695713A1 (fr) * 1992-09-17 1994-03-18 Snecma Système d'injection aérodynamique à prémélange.

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0893650A2 (de) * 1997-07-23 1999-01-27 General Electric Company Vergaser mit multiplen Verwirbelungsvorrichtungen
EP0893650A3 (de) * 1997-07-23 1999-05-12 General Electric Company Vergaser mit multiplen Verwirbelungsvorrichtungen

Also Published As

Publication number Publication date
US5651252A (en) 1997-07-29
FR2730555B1 (fr) 1997-03-14
FR2730555A1 (fr) 1996-08-14

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